Advances in Spacecraft Technologies by Jason Hall

By Jason Hall

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Han, J. W. & Li, H. R. (2007). Space docking hybrid simulation prototype experiment system. Chinese Journal of Mechanical Engineering. ; Yang, L. & Qu, G. J. (2004). Dynamics analysis and simulation of spacecraft docking mechanism. 2004, pp. 38-42 (in Chinese) 34 Advances in Spacecraft Technologies Zhang, C. F. (1999). Study on Six-Degree-of-Freedom simulation for docking. 1, Jan. 70-74 (in Chinese) Zhang, S. Y. (2006). Research on force control of hydraulic driven 6-DOF parallel robot. Ph. D.

A new procedural for the integration of the HIL simulation system for on-orbit docking. 769-773, ISBN Shenzhen Institute of Advanced Technology, Mar. 2007, IEEE, Shenzhen, China. Chang, T. ; Cong, D. ; Ye, Z. M. & Han, J. W. (2007b). Time problems in HIL simulation for on-orbit docking and compensation. 841-846. IEEE Industrial Electronics (IE) Chapter & Harbin Institute of Technology, Ma. 2007, Harbin, China, Chang, T. ; Cong, D. ; Ye, Z. M. & Han, J. W. (2007c). Electro-hydraulic servo control system design of HIL simulator for spacecraft on-orbit docking.

However, while it is accurate that the launch mass is typically reduced this does not directly result in a reduced launch vehicle cost as the reduction may not be sufficient to allow the use of a less capable, and hence lower cost, launch vehicle. As such the launch cost is only reduced if the reduced launch mass allows a smaller launch vehicle to be used, meaning that launch cost varies as a step function while launch mass linearly increases. Finally, it should be noted that if the total mission cost is high, say, 500+ M€ then 45 Solar Sailing: Applications and Technology Advancement reducing the launch mass cost by 10 – 20 M€ is a cost saving of order 2 – 4 %, which may not be considered a good cost/risk ratio for the project and indeed, the cost saving may be insufficient to pay for the additional development of the technology.

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